EP3018445A1 - Eingekapselte kapazitätssonde mit einem flexiblen elektrischen kabel für einen gasturbinenmotor - Google Patents

Eingekapselte kapazitätssonde mit einem flexiblen elektrischen kabel für einen gasturbinenmotor Download PDF

Info

Publication number
EP3018445A1
EP3018445A1 EP15193505.3A EP15193505A EP3018445A1 EP 3018445 A1 EP3018445 A1 EP 3018445A1 EP 15193505 A EP15193505 A EP 15193505A EP 3018445 A1 EP3018445 A1 EP 3018445A1
Authority
EP
European Patent Office
Prior art keywords
circuit board
board sensor
gas turbine
capacitance probe
liner
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Granted
Application number
EP15193505.3A
Other languages
English (en)
French (fr)
Other versions
EP3018445B1 (de
Inventor
Kevin Ford
Eli WARREN
Corey A. BENOIT
Edward F. Dreger
Erik D. RICE
Mark W. Costa
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Raytheon Technologies Corp
Original Assignee
United Technologies Corp
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by United Technologies Corp filed Critical United Technologies Corp
Publication of EP3018445A1 publication Critical patent/EP3018445A1/de
Application granted granted Critical
Publication of EP3018445B1 publication Critical patent/EP3018445B1/de
Active legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Images

Classifications

    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01D—MEASURING NOT SPECIALLY ADAPTED FOR A SPECIFIC VARIABLE; ARRANGEMENTS FOR MEASURING TWO OR MORE VARIABLES NOT COVERED IN A SINGLE OTHER SUBCLASS; TARIFF METERING APPARATUS; MEASURING OR TESTING NOT OTHERWISE PROVIDED FOR
    • G01D5/00—Mechanical means for transferring the output of a sensing member; Means for converting the output of a sensing member to another variable where the form or nature of the sensing member does not constrain the means for converting; Transducers not specially adapted for a specific variable
    • G01D5/12—Mechanical means for transferring the output of a sensing member; Means for converting the output of a sensing member to another variable where the form or nature of the sensing member does not constrain the means for converting; Transducers not specially adapted for a specific variable using electric or magnetic means
    • G01D5/14—Mechanical means for transferring the output of a sensing member; Means for converting the output of a sensing member to another variable where the form or nature of the sensing member does not constrain the means for converting; Transducers not specially adapted for a specific variable using electric or magnetic means influencing the magnitude of a current or voltage
    • G01D5/24—Mechanical means for transferring the output of a sensing member; Means for converting the output of a sensing member to another variable where the form or nature of the sensing member does not constrain the means for converting; Transducers not specially adapted for a specific variable using electric or magnetic means influencing the magnitude of a current or voltage by varying capacitance
    • G01D5/241—Mechanical means for transferring the output of a sensing member; Means for converting the output of a sensing member to another variable where the form or nature of the sensing member does not constrain the means for converting; Transducers not specially adapted for a specific variable using electric or magnetic means influencing the magnitude of a current or voltage by varying capacitance by relative movement of capacitor electrodes
    • G01D5/2417—Mechanical means for transferring the output of a sensing member; Means for converting the output of a sensing member to another variable where the form or nature of the sensing member does not constrain the means for converting; Transducers not specially adapted for a specific variable using electric or magnetic means influencing the magnitude of a current or voltage by varying capacitance by relative movement of capacitor electrodes by varying separation
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D17/00—Regulating or controlling by varying flow
    • F01D17/02—Arrangement of sensing elements
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D21/00—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for
    • F01D21/003—Arrangements for testing or measuring
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/02—Blade-carrying members, e.g. rotors
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/26—Rotors specially for elastic fluids
    • F04D29/32—Rotors specially for elastic fluids for axial flow pumps
    • F04D29/321—Rotors specially for elastic fluids for axial flow pumps for axial flow compressors
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/26—Rotors specially for elastic fluids
    • F04D29/32—Rotors specially for elastic fluids for axial flow pumps
    • F04D29/325—Rotors specially for elastic fluids for axial flow pumps for axial flow fans
    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01B—MEASURING LENGTH, THICKNESS OR SIMILAR LINEAR DIMENSIONS; MEASURING ANGLES; MEASURING AREAS; MEASURING IRREGULARITIES OF SURFACES OR CONTOURS
    • G01B7/00—Measuring arrangements characterised by the use of electric or magnetic techniques
    • G01B7/14—Measuring arrangements characterised by the use of electric or magnetic techniques for measuring distance or clearance between spaced objects or spaced apertures
    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
    • G01M15/00—Testing of engines
    • G01M15/14—Testing gas-turbine engines or jet-propulsion engines
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
    • F01D11/14—Adjusting or regulating tip-clearance, i.e. distance between rotor-blade tips and stator casing
    • F01D11/20—Actively adjusting tip-clearance
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2220/00—Application
    • F05D2220/30—Application in turbines
    • F05D2220/32—Application in turbines in gas turbines
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/83—Testing, e.g. methods, components or tools therefor
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

Definitions

  • This disclosure generally relates to gas turbine engines.
  • this disclosure relates to a system for measuring blade tip clearances relative to a fan case.
  • gas turbine engines for generating energy and propulsion.
  • Such engines include a fan, compressor, combustor and turbine provided in serial fashion, forming an engine core and arranged along a central longitudinal axis. Air enters the gas turbine engine through the fan and is pressurized in the compressor. This pressurized air is mixed with fuel in the combustor. The fuel-air mixture is then ignited, generating hot combustion gases that flow downstream to the turbine. The turbine is driven by the exhaust gases and mechanically powers the compressor and fan via an internal shaft. Energy from the combustion gases not used by the turbine is discharged through an exhaust nozzle, producing thrust to power the aircraft.
  • Gas turbine engines contain an engine core and fan surrounded by a fan case, forming part of a nacelle.
  • the nacelle is a housing that contains the engine.
  • the fan is positioned forward of the engine core and within the fan case.
  • the engine core is surrounded by an engine core cowl and the area between the nacelle and the engine core cowl is functionally defined as a fan duct.
  • the fan duct is substantially annular in shape to accommodate the airflow from the fan and around the engine core cowl.
  • the airflow through the fan duct known as bypass air, travels the length of the fan duct and exits at the aft end of the fan duct at an exhaust nozzle.
  • the fan of gas turbine engines In addition to thrust generated by combustion gasses, the fan of gas turbine engines also produces thrust by accelerating and discharging ambient air through the exhaust nozzle.
  • Various parts of the gas turbine engine generate heat while operating, including the compressor, combustor, turbine, central rotating shaft and fan. To maintain proper operational temperatures, excess heat is often removed from the engine via oil coolant loops, including air/oil or fuel/oil heat exchangers, and dumped into the bypass airflow for removal from the system.
  • the fan includes a number of blades arranged radially from the central longitudinal axis.
  • the blades rotate about the central longitudinal axis when in operation.
  • Each blade has a tip located at the blade's extreme end, distal to the central longitudinal axis.
  • As the fan rotates, each blade will pass at a distance from a point along the fan case.
  • Certain distances, or tolerance levels, are desirable for different gas turbine engine performance characteristics. If such a tolerance level is not achieved, conditions adverse to gas turbine engine efficiency may result, including increased turbulence, internal drag or flow around the fan rather than through the fan.
  • a gap measuring assembly which may include a rotating member, an expandable member relative to the rotating member and defining a gap therebetween, a circuit board sensor mounted to the expandable member, the circuit board sensor including a metallic plate disposed within an insulating material and a housing, and a soft lead extending from the housing and being embedded in the expandable member.
  • the circuit board sensor may include one or more capacitors.
  • the circuit board sensor may be in electronic communication with the soft lead.
  • the rotating member may be a blade.
  • the expandable member may be a thermally conforming liner.
  • the thermally conforming liner may be able to expand in response to thermal or mechanical changes.
  • the insulating material may be a polymer.
  • the insulating material may be a ceramic.
  • the housing may be made from an electrically conductive material.
  • the gap measuring assembly may be able to sense a distance at which a blade passes relative to the liner.
  • the present disclosure also provides a gas turbine engine, which may include a fan located at the axially forward end of the gas turbine engine and axially forward of a compressor, the compressor located axially forward of a turbine, the turbine mechanically connected to the fan and the compressor, a capacitance probe including a circuit board sensor having a metallic plate disposed within an insulating material, the circuit board sensor disposed within a housing, the capacitance probe, circuit board sensor and housing adapted to monitor a tolerance of the gas turbine engine.
  • the circuit board sensor may include one or more capacitors.
  • the circuit board sensor may be in electronic communication with one or more soft leads.
  • a liner may be positioned proximate to the fan, wherein the one or more soft leads are embedded in the liner.
  • the capacitance probe may be attached to the liner.
  • the insulating material may be a polymer.
  • the insulating material may be a ceramic.
  • the housing may be made from an electrically conductive material.
  • the present disclosure further provides a method for measuring tip clearance relative to a static structure of a gas turbine engine that may include attaching a capacitance probe to a liner, the capacitance probe including a circuit board sensor having a metallic plate disposed within an insulating material, the capacitance probe disposed within a housing, the capacitance probe able to sense a distance at which a blade tip passes, rotating a fan about a central longitudinal axis, the fan having a plurality of blades, each blade having a tip, and sensing a minimum distance between the tip and the capacitance probe when the tip travels past the sensor.
  • the circuit board sensor may further include one or more capacitors, and the circuit board sensor may be in electronic communication with one or more soft leads.
  • the gas turbine engine 10 includes a compressor 11, combustor 12 and turbine 13, known as the engine core 14, lying along a central longitudinal axis 15, and surrounded by an engine core cowl 16.
  • the compressor 11 is connected to the turbine 13 via a central rotating shaft 17. Additionally, in a typical multi-spool design, plural turbine 13 sections are connected to, and drive, corresponding plural sections of the compressor 11 and a fan 18 by way of central rotating shaft 17, enabling increased compression efficiency.
  • the fan 18 is located at the axially forward end of the gas turbine engine 10, and axially forward of the compressor 11.
  • the compressor 11 is located axially forward of the turbine 13.
  • ambient air enters the compressor 11 at an inlet 19, is pressurized, and is then directed to the combustor 12, mixed with fuel and combusted. This generates combustion gases that flow downstream to the turbine 13, which extracts kinetic energy from the exhausted combustion gases.
  • a nacelle 20 is a substantially cylindrical housing around the gas turbine engine 10. As best understood through FIG. 2 in conjunction with FIG. 3 , the interior surface of the nacelle 20 consists of a fan cowl 22, which surrounds the fan 18 and engine core cowl 16.
  • a fan duct 24 is functionally defined by the axially extending area between the engine core cowl 16 and the fan cowl 22.
  • the fan duct 24 is substantially annular in shape to accommodate the airflow produced by the fan 18. This airflow travels the length of the fan duct 24 and exits downstream at a fan nozzle 26.
  • the fan nozzle 26 is located at the downstream exit of the fan duct 24, as shown in FIG. 2 .
  • the fan 18, engine core 14 and nacelle 20 may be centered on a central longitudinal axis 15. Thrust is produced both by the ambient air accelerated aft by the fan 18 through the fan duct 24 and by exhaust gasses exiting from the engine core 14.
  • the fan 18 may include a plurality of blades 32 radially extending from the central longitudinal axis 15, as best shown in FIG. 3 .
  • Blades 32 are disposed within a fan case 34 and rotate relative thereto in close proximity. More specifically, each blade 32 includes a tip 33 at the blade 32 extreme end, distal to the central longitudinal axis 15. As the fan 18 rotates, each tip 33 will pass at a distance from a point on the fan case 34. Certain distances, or tolerance levels, are desirable for different gas turbine engine 10 performance characteristics. If a desired tolerance level is not achieved, conditions adverse to gas turbine engine 10 efficiency may result, including increased turbulence, internal drag, or flow around the fan 18 rather than through the fan 18. Airflow can even travel upstream around the fan 18, from the fan duct 24 to the atmosphere. Accordingly, it is important to accurately monitor the distance between the tip 33 and the fan case 34 to maintain such tolerances.
  • a capacitance probe 36 may be used to monitor the distance between the tip 33 and the fan case 34 or a liner 37 as the fan 18 rotates, as shown in FIG. 4 .
  • the capacitance probe 36 may also be described as a gap measuring assembly.
  • various parts of a gas turbine engine 10 may expand due to the heat generated and absorbed during its operation.
  • a malleable or thermally conforming liner 37 may be disposed in proximity to the fan case 34, and may form a section of the fan case 34 or exist as an independent part.
  • the liner 37 may expand or contract radially during gas turbine engine 10 operation in response to thermal changes.
  • the blades 32 may also expand in response to thermal changes, and the blades 32 and liner 37 may expand by similar or identical amounts. In this manner, a desired distance between the tip 33 and the liner 37 may be maintained.
  • the liner 37 may be constructed of a synthetic fiber, a para-aramid synthetic fiber, Kevlar®, a composite material, a metal or a polymer. Heat from combustion, friction between gas turbine engine 10 components or direct contact between a blade 32 and the liner 37 may be absorbed into the liner 37, causing it to radially expand.
  • the present disclosure goes further by associating the capacitance probe 36 with the liner 37 in a manner which minimizes space requirements.
  • This inventive contribution is significant as the capacitance probe 36 must do so within the confines of a dynamically changing material while not affecting the overall size envelope of the liner 37 itself.
  • the capacitance probe 36 may be attached directly to the liner 37.
  • the attachment mechanism may include rivets, bolts, screws, adhesives, clips or other methods as explained in more detail below.
  • the attached capacitance probe 36 may travel with the liner 37. In this way, the capacitance probe 36 can record a more accurate distance measurement.
  • the capacitance probe 36 may also detect a distance between other rotating members, including compressor 11 blades or turbine 13 blades, and other static structures, including compressor 11 cases or turbine 13 cases.
  • the capacitance probe 36 may include a circuit board sensor 38, as best shown in FIGS. 5-6 .
  • the circuit board sensor 38 may include a plate 40 and one or more capacitors 42.
  • the plate 40 may be made of metal and be encapsulated within an insulating material 44.
  • the insulating material 44 may be a polymer, epoxy, ceramic, metal or other insulating material, and may have electrical, thermal or vibrational insulating properties.
  • the plate 40 may be a metal such as copper, although other materials are certainly possible.
  • the capacitance probe 36 may further include an annular ring pad 39, a via 41 and a circuit track 43, as best shown in FIG. 6 .
  • the annular ring pad 39 may be operatively associated with the plate 40 through the via 41.
  • the circuit track 43 may allow the one or more capacitors 42 to be in electronic communication with the annular ring pad 39.
  • the circuit board sensor 38 construction allows an easier replacement or modification of the circuit board sensor 38 without damaging the capacitance probe 36. Additionally, it may be possible to adjust the capacitance of the circuit board sensor 38 according to the task at hand by adding, removing or adjusting capacitors 42 on the circuit board sensor 38.
  • the capacitance probe 36 may be disposed within a housing 46, as shown in FIG. 6 , made from a metal, ceramic, polymer or other electrically conductive material.
  • the housing 46 may include provisions for attachment to the liner 37, as indicated above.
  • the capacitance probe 36 may be attached to the liner 37 at a point where the tip 33 passes by as the fan 18 rotates as to better monitor actual tolerances and tip 33 clearance.
  • the capacitance between the circuit board sensor 38 and tip 33 will change based on the change in distance. This difference in capacitance may then be converted to a voltage and recorded for use in clearance control systems or redesign efforts.
  • soft leads 48 may be in electrical communication with the circuit board sensor 38 in the capacitance probe 36.
  • the soft leads 48 may be soldered to the capacitors 42, or to another part of the circuit board sensor 38.
  • the soft leads 48 may exist free from any external tubing or routing structure, allowing the soft leads 48 to have a lower weight, reduced size and increased flexibility. The lack of an external structure may also allow for more efficient and compact soft lead 48 routing and egress.
  • the soft leads 48 may also be embedded in the liner 37, and may move with the liner 37 as it thermally expands.
  • the soft leads 48 may carry electronic information from the circuit board sensor 38 to another electronic device. Additionally, the soft leads 48 may further include a capacitance-based temperature compensation system for more accurate distance readings between the tip 33 and the fan case 34.
  • the capacitance probe 36 may be disposed within the housing 46, as shown in FIG. 7 .
  • the housing 46 may include a housing base 50 and a housing cap 51.
  • the housing base 50 may allow the soft leads 48 to pass through, such as by providing a notch 52 or other void therein as shown in FIG. 7 .
  • the housing cap 51 may attach to the liner 37 via one or more fasteners 53, such as rivets or through other attachment methods.
  • the housing cap 51 may also attach to the housing base 50.
  • a method for measuring tip clearance relative to a fan case can be understood by referencing the flowchart in FIG. 8 .
  • the method may include attaching a capacitance probe to a liner, the capacitance probe including a circuit board sensor having a metallic plate disposed within an insulating material, the capacitance probe disposed within a housing, and the capacitance probe able to sense a distance at which a blade tip passes 100, rotating a fan about a central longitudinal axis, the fan having a plurality of blades, each blade having a tip 102, sensing a minimum distance between the tip and the capacitance probe when the tip travels past the sensor 104, and the circuit board sensor may further include one or more capacitors, and the circuit board sensor may be in electronic communication with one or more soft leads 106.
  • the present disclosure sets forth a capacitance probe 36 system which can find industrial applicability in a variety of settings.
  • the disclosure may be advantageously employed in sensing parameters and characteristics within a gas turbine engine 10.
  • the capacitance probe 36 can be used to measure a distance between the tip 33 and the fan case 34 during the operation of the gas turbine engine 10. If a desired tolerance level is not achieved, conditions adverse to gas turbine engine 10 efficiency may result, including increased turbulence, internal drag or flow around the fan 18 rather than through the fan 18. Accordingly, it is important to accurately monitor the distance between the tip 33 and the fan case 34.
  • the capacitance probe 36 system of the present disclosure may employ soft leads 48 in electronic communication with a circuit board sensor 38 in the capacitance probe 36.
  • the soft leads 48 allow the entire lead apparatus to be smaller, lighter and more flexible.
  • the capacitance probe 36 may also attach to the liner 37. As the liner 37 expands radially in response to thermal energy generated during operation, the capacitance probe 36 may travel with the liner 37 to increase measurement accuracy.
  • the capacitance probe 36 system of the present disclosure contributes to a gas turbine engine's 10 continued and efficient operation.
  • the disclosed capacitance probe 36 system may be original equipment on new gas turbine engines 10, or added as a retrofit to existing gas turbine engines 10. While the foregoing has been described as a system for monitoring the distance between the tip 33 and the fan case 34, it can be described with equal accuracy as a gap measuring assembly.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • General Physics & Mathematics (AREA)
  • Power Engineering (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Measurement Of Length, Angles, Or The Like Using Electric Or Magnetic Means (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Testing Of Engines (AREA)
EP15193505.3A 2014-11-06 2015-11-06 Bläsergehäuse montage mit kapazitiver sonde zur messung des turbinenschaufelspitenspiels und entsprechendes verfahren zur messung des turbinenschaufelspitenspiels Active EP3018445B1 (de)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US201462076289P 2014-11-06 2014-11-06

Publications (2)

Publication Number Publication Date
EP3018445A1 true EP3018445A1 (de) 2016-05-11
EP3018445B1 EP3018445B1 (de) 2019-01-02

Family

ID=54539864

Family Applications (1)

Application Number Title Priority Date Filing Date
EP15193505.3A Active EP3018445B1 (de) 2014-11-06 2015-11-06 Bläsergehäuse montage mit kapazitiver sonde zur messung des turbinenschaufelspitenspiels und entsprechendes verfahren zur messung des turbinenschaufelspitenspiels

Country Status (2)

Country Link
US (1) US10436612B2 (de)
EP (1) EP3018445B1 (de)

Cited By (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3366889A1 (de) * 2017-02-23 2018-08-29 United Technologies Corporation Gasturbinen gebäsesonde
CN108731907A (zh) * 2018-09-05 2018-11-02 西安远方航空技术发展有限公司 一种复合测量耙
EP3438636A1 (de) * 2017-08-03 2019-02-06 United Technologies Corporation Verschleissanzeiger mit elektrischem widerstand
EP3453844A1 (de) * 2017-09-12 2019-03-13 United Technologies Corporation Flacher eingebetteter blattspitzenabstandssensor
EP3495624A3 (de) * 2017-12-05 2019-07-31 United Technologies Corporation Vollintegrierte epoxidkappensonde
US10371497B2 (en) 2017-12-05 2019-08-06 United Technologies Corporation Fully integral epoxy cap probe
US20200191610A1 (en) * 2018-12-12 2020-06-18 Weston Aerospace Limited Probe for monitoring a moving engine element
CN115143860A (zh) * 2022-06-22 2022-10-04 中国航发贵州黎阳航空动力有限公司 风扇叶片叶尖圆弧测具及测试方法

Families Citing this family (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB201401111D0 (en) * 2014-01-23 2014-03-12 Rolls Royce Plc A method of inspecting the fan track liner of a gas turbine engine
JP7116541B2 (ja) * 2017-11-30 2022-08-10 三菱重工業株式会社 回転機械の翼の状態の監視センサ及びセンサの位置調節方法
US10557373B2 (en) 2017-12-05 2020-02-11 United Technologies Corporation Low profile embedded blade tip clearance probe assembly
US10641595B2 (en) 2018-04-09 2020-05-05 United Technologies Corporation Low profile triaxial blade tip clearance probe assembly with driven guard
US10738645B2 (en) * 2018-08-31 2020-08-11 Raytheon Technologies Corporation Embedded triaxial epoxy cap probe

Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2842738A (en) * 1956-04-05 1958-07-08 Ford Motor Co Capacitance probe
EP0246576A1 (de) * 1986-05-23 1987-11-25 Mtu Motoren- Und Turbinen-Union MàœNchen Gmbh Kapazitives Messsystem
US5140494A (en) * 1989-03-07 1992-08-18 Rolls-Royce Plc Gas turbine engine tip clearance sensors
US5166626A (en) * 1990-05-29 1992-11-24 General Electric Company Electrical capacitance clearanceometer
US5973502A (en) * 1996-06-26 1999-10-26 Thermacoax Sas Capacitive sensor including a coaxial cable and a probe
US20090128166A1 (en) * 2007-11-21 2009-05-21 Rolls-Royce Plc Apparatus to measure the clearance between a first component and a second component
EP2505779A2 (de) * 2011-03-28 2012-10-03 General Electric Company Verfahren und System zum Prüfen des Schaufelspitzenabstands
CN103673863A (zh) * 2013-12-03 2014-03-26 浙江中欣动力测控技术有限公司 一种电容传感器

Family Cites Families (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB8707187D0 (en) * 1987-03-25 1987-04-29 Hughes Ltd Stewart Monitoring of foreign object in engines

Patent Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2842738A (en) * 1956-04-05 1958-07-08 Ford Motor Co Capacitance probe
EP0246576A1 (de) * 1986-05-23 1987-11-25 Mtu Motoren- Und Turbinen-Union MàœNchen Gmbh Kapazitives Messsystem
US5140494A (en) * 1989-03-07 1992-08-18 Rolls-Royce Plc Gas turbine engine tip clearance sensors
US5166626A (en) * 1990-05-29 1992-11-24 General Electric Company Electrical capacitance clearanceometer
US5973502A (en) * 1996-06-26 1999-10-26 Thermacoax Sas Capacitive sensor including a coaxial cable and a probe
US20090128166A1 (en) * 2007-11-21 2009-05-21 Rolls-Royce Plc Apparatus to measure the clearance between a first component and a second component
EP2505779A2 (de) * 2011-03-28 2012-10-03 General Electric Company Verfahren und System zum Prüfen des Schaufelspitzenabstands
CN103673863A (zh) * 2013-12-03 2014-03-26 浙江中欣动力测控技术有限公司 一种电容传感器

Cited By (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US10690475B2 (en) 2017-02-23 2020-06-23 Raytheon Technologies Corporation Encapsulated fan cap probe
EP3366889A1 (de) * 2017-02-23 2018-08-29 United Technologies Corporation Gasturbinen gebäsesonde
US11441444B2 (en) 2017-08-03 2022-09-13 Raytheon Technologies Corporation Electrical resistance wear indicator
EP3438636A1 (de) * 2017-08-03 2019-02-06 United Technologies Corporation Verschleissanzeiger mit elektrischem widerstand
US10760445B2 (en) 2017-08-03 2020-09-01 Raytheon Technologies Corporation Electrical resistance wear indicator
US10808570B2 (en) 2017-09-12 2020-10-20 Raytheon Technologies Corporation Low profile embedded blade tip clearance sensor
EP3453844A1 (de) * 2017-09-12 2019-03-13 United Technologies Corporation Flacher eingebetteter blattspitzenabstandssensor
US10371497B2 (en) 2017-12-05 2019-08-06 United Technologies Corporation Fully integral epoxy cap probe
EP3495624A3 (de) * 2017-12-05 2019-07-31 United Technologies Corporation Vollintegrierte epoxidkappensonde
CN108731907A (zh) * 2018-09-05 2018-11-02 西安远方航空技术发展有限公司 一种复合测量耙
CN108731907B (zh) * 2018-09-05 2024-02-27 西安远方航空技术发展有限公司 一种复合测量耙
US20200191610A1 (en) * 2018-12-12 2020-06-18 Weston Aerospace Limited Probe for monitoring a moving engine element
CN115143860A (zh) * 2022-06-22 2022-10-04 中国航发贵州黎阳航空动力有限公司 风扇叶片叶尖圆弧测具及测试方法

Also Published As

Publication number Publication date
EP3018445B1 (de) 2019-01-02
US20160195411A1 (en) 2016-07-07
US10436612B2 (en) 2019-10-08

Similar Documents

Publication Publication Date Title
EP3018445B1 (de) Bläsergehäuse montage mit kapazitiver sonde zur messung des turbinenschaufelspitenspiels und entsprechendes verfahren zur messung des turbinenschaufelspitenspiels
CN109416029B (zh) 从复合飞行器发动机部件收集能量
EP2610599B1 (de) Temperaturmessvorrichtung und Verfahren zum Aufbau davon
EP2818839A2 (de) Thermoelementfühler
EP3431706B1 (de) Verschleissanzeigesensor und messverfahren des turbinenschaufelspitzenspiels
CA2904309A1 (en) Axial turbomachine compressor external casing with seal
EP3203039A1 (de) Kühlsystem für ein gasturbinentriebwerk, zugehöriges gasturbinentriebwerk und verfahren zur kühlung
US11092083B2 (en) Pressure sensor assembly for a turbine engine
JP6937580B2 (ja) エンジンのための静電気ダストセンサ
US20150152743A1 (en) Method for minimizing the gap between a rotor and a housing
EP3267023A1 (de) Gasturbinentriebwerkheckkonus
US11692871B2 (en) System and method for disposable imaging system
US10145306B2 (en) Heat shield for gas turbine engine gearbox
US9320181B1 (en) System and method for dissipating thermal energy away from electronic components in a rotatable shaft
EP3418703B1 (de) Lufttemperatursensor
US11624662B2 (en) Exhaust gas temperature sensor
US11774427B2 (en) Methods and apparatus for monitoring health of fuel oxygen conversion unit
Sheard et al. Electromechanical measurement of turbomachinery blade tip-to-casing running clearance
US10545057B2 (en) Air temperature sensor and method of reducing error
CN110805478A (zh) 具有衬套的空气温度传感器
Smallwood et al. Thermal and structural characterization of A rotating detonation rocket engine
CN117231369A (zh) 用于燃气涡轮发动机的绝缘组件
BR102022019594A2 (pt) Dispositivo de turbina
Alford et al. Fast Thermocouples as Control-System Elements Sensing Exhaust-Gas Temperatures in Aircraft Gas Turbines
Long et al. Application of a Miniature Telemetry System in a Small Gas Turbine Engine

Legal Events

Date Code Title Description
PUAI Public reference made under article 153(3) epc to a published international application that has entered the european phase

Free format text: ORIGINAL CODE: 0009012

AK Designated contracting states

Kind code of ref document: A1

Designated state(s): AL AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO RS SE SI SK SM TR

AX Request for extension of the european patent

Extension state: BA ME

RAP1 Party data changed (applicant data changed or rights of an application transferred)

Owner name: UNITED TECHNOLOGIES CORPORATION

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: REQUEST FOR EXAMINATION WAS MADE

17P Request for examination filed

Effective date: 20161111

RBV Designated contracting states (corrected)

Designated state(s): AL AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO RS SE SI SK SM TR

GRAP Despatch of communication of intention to grant a patent

Free format text: ORIGINAL CODE: EPIDOSNIGR1

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: GRANT OF PATENT IS INTENDED

RIC1 Information provided on ipc code assigned before grant

Ipc: G01D 5/241 20060101ALI20180628BHEP

Ipc: F01D 17/02 20060101ALI20180628BHEP

Ipc: G01B 7/14 20060101AFI20180628BHEP

Ipc: F01D 11/20 20060101ALN20180628BHEP

INTG Intention to grant announced

Effective date: 20180712

GRAS Grant fee paid

Free format text: ORIGINAL CODE: EPIDOSNIGR3

GRAA (expected) grant

Free format text: ORIGINAL CODE: 0009210

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: THE PATENT HAS BEEN GRANTED

AK Designated contracting states

Kind code of ref document: B1

Designated state(s): AL AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO RS SE SI SK SM TR

REG Reference to a national code

Ref country code: GB

Ref legal event code: FG4D

REG Reference to a national code

Ref country code: CH

Ref legal event code: EP

Ref country code: AT

Ref legal event code: REF

Ref document number: 1084943

Country of ref document: AT

Kind code of ref document: T

Effective date: 20190115

REG Reference to a national code

Ref country code: IE

Ref legal event code: FG4D

REG Reference to a national code

Ref country code: DE

Ref legal event code: R096

Ref document number: 602015022660

Country of ref document: DE

REG Reference to a national code

Ref country code: NL

Ref legal event code: MP

Effective date: 20190102

REG Reference to a national code

Ref country code: LT

Ref legal event code: MG4D

REG Reference to a national code

Ref country code: AT

Ref legal event code: MK05

Ref document number: 1084943

Country of ref document: AT

Kind code of ref document: T

Effective date: 20190102

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: NL

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20190102

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: ES

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20190102

Ref country code: FI

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20190102

Ref country code: PT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20190502

Ref country code: SE

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20190102

Ref country code: NO

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20190402

Ref country code: PL

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20190102

Ref country code: LT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20190102

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: HR

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20190102

Ref country code: RS

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20190102

Ref country code: BG

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20190402

Ref country code: GR

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20190403

Ref country code: IS

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20190502

Ref country code: LV

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20190102

REG Reference to a national code

Ref country code: DE

Ref legal event code: R097

Ref document number: 602015022660

Country of ref document: DE

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: SK

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20190102

Ref country code: EE

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20190102

Ref country code: DK

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20190102

Ref country code: AT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20190102

Ref country code: IT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20190102

Ref country code: AL

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20190102

Ref country code: RO

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20190102

Ref country code: CZ

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20190102

PLBE No opposition filed within time limit

Free format text: ORIGINAL CODE: 0009261

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: NO OPPOSITION FILED WITHIN TIME LIMIT

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: SM

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20190102

26N No opposition filed

Effective date: 20191003

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: SI

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20190102

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: TR

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20190102

REG Reference to a national code

Ref country code: CH

Ref legal event code: PL

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: CH

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20191130

Ref country code: LI

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20191130

Ref country code: LU

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20191106

Ref country code: MC

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20190102

REG Reference to a national code

Ref country code: BE

Ref legal event code: MM

Effective date: 20191130

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: IE

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20191106

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: BE

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20191130

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: CY

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20190102

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: HU

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT; INVALID AB INITIO

Effective date: 20151106

Ref country code: MT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20190102

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: MK

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20190102

REG Reference to a national code

Ref country code: DE

Ref legal event code: R081

Ref document number: 602015022660

Country of ref document: DE

Owner name: RAYTHEON TECHNOLOGIES CORPORATION (N.D.GES.D.S, US

Free format text: FORMER OWNER: UNITED TECHNOLOGIES CORPORATION, FARMINGTON, CONN., US

P01 Opt-out of the competence of the unified patent court (upc) registered

Effective date: 20230520

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: GB

Payment date: 20231019

Year of fee payment: 9

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: FR

Payment date: 20231019

Year of fee payment: 9

Ref country code: DE

Payment date: 20231019

Year of fee payment: 9